WO2012016790A1 - Component of a turbine with leaf seals and method for sealing against leakage between a vane and a carrier element - Google Patents

Component of a turbine with leaf seals and method for sealing against leakage between a vane and a carrier element Download PDF

Info

Publication number
WO2012016790A1
WO2012016790A1 PCT/EP2011/061641 EP2011061641W WO2012016790A1 WO 2012016790 A1 WO2012016790 A1 WO 2012016790A1 EP 2011061641 W EP2011061641 W EP 2011061641W WO 2012016790 A1 WO2012016790 A1 WO 2012016790A1
Authority
WO
WIPO (PCT)
Prior art keywords
vane
turbine
carrier element
component
seal
Prior art date
Application number
PCT/EP2011/061641
Other languages
French (fr)
Inventor
Stephen Batt
Original Assignee
Siemens Aktiengesellschaft
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Priority to RU2013109413/06A priority Critical patent/RU2583487C2/en
Priority to CN201180038491.3A priority patent/CN103052766B/en
Priority to US13/812,153 priority patent/US9506374B2/en
Priority to EP11732428.5A priority patent/EP2564032B1/en
Publication of WO2012016790A1 publication Critical patent/WO2012016790A1/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • F05D2240/57—Leaf seals

Definitions

  • the present invention relates to a component of a turbine. It further relates to a method for sealing against leakage be ⁇ tween a vane and a carrier element of a turbine component.
  • the air leakage between a turbine vane axial face and the corresponding feature of the carrier ring is required to be limited to a minimum.
  • the turbine vane and carrier rings are subjected to thermal and mechanical loads which induce dis ⁇ tortion and relative movement. Therefore, leakage between a turbine vane and the corresponding feature of the carrier ring may occur.
  • a leaf seal support for a gas turbine en- gine nozzle vane is described.
  • the turbine nozzle assembly includes a plurality of segments joint together to form an outer band and a plurality of segments joined together to form an inner band. At least to one airfoil is positioned be ⁇ tween the outer and inner bands.
  • a leaf seal is attached to each inner band segment by at least one pin member and a leaf seal is attached to each outer band segment by at least one pin member.
  • a turbine seal is dis ⁇ closed.
  • the turbine seal includes a first arcuate segment de ⁇ fining a flowpath boundary between combustion gases and air and includes a radially outwardly extending rail at one end thereof.
  • a second arcuate segment is disposed coaxially with the first segment for defining a continuation of the flowpath boundary. It has a radially extending face adjoining the rail.
  • a leaf seal bridges the rail and the face for sealing leakage there between.
  • a plurality of pins extended through the leaf seal for providing the mounting to the rail.
  • an assembly for providing a seal at an aft end of a combustor liner for a gas turbine engine is de ⁇ scribed.
  • the sealing assembly includes a substantially annu- lar first sealing member positioned between an aft portion of a support member and the liner aft end so as to seat on a designated surface portion of the liner aft end.
  • a substan ⁇ tially annular second sealing member is positioned between the support member aft portion and a turbine nozzle located downstream of the liner aft end so as to seat on a designated surface portion of the support member aft portion.
  • the first and second sealing members are maintained in their respective seating positions as the support member aft portion moves ra ⁇ dially or axially with respect to the liner aft end and ra- dially or axially with respect to the turbine nozzle.
  • the first and second sealing members allow for axially and ra ⁇ dially movement of the adjacent components.
  • a sealing arrangement for gas turbines comprises a number of openings through which a fluid can pass the sealing member.
  • a seal which comprises a first and a second component is disclosed. The seal is applied to a com ⁇ bustion chamber for a gas turbine. It comprises a spring load which provides a seal also in the case of vibrations in the combustion chamber. The seal is further applied to the seal ⁇ ing between adjacent stationary blade platforms in gas turbines. The seal comprises a number of openings for leading a fluid through the seal .
  • US 5,343,694 a gas turbine nozzle including a plurality of nozzle segments having a pair of nozzle vanes supported by inner and outer shroud segments is disclosed.
  • the outer shroud segment includes a generally axially extending plat ⁇ form with a circumferentially extending seal member attached to the upstream end thereof to seal with the combustor liner flange against the leakage there between. Moreover, a ra ⁇ dially extending circumferential projection is attached to the downstream end of the platform for providing an engagement surface for a W seal to prevent leakage between the outer rotor casing and the shroud segment.
  • a turbine nozzle segment including a band having a plurality of tabs is dis ⁇ closed.
  • An airfoil extending from the band and a support structure attached to the tabs is described.
  • the support structure has a plurality of biasing structures.
  • a gas turbine nozzle arrangement is dis ⁇ closed. It comprises at least one seal strip which is present between a radially outer surface of a carrier ring section and inner surface of an inner platform and comprises openings for allowing cooling fluid to flow through the seal strip.
  • the document EP 1 296 023 Al discloses a devise for holding strip sealing gaskets on a turbo machine nozzle.
  • the first objective is solved by a component as claimed in claim 1.
  • the second objective is solved by a method as claimed in claim 12.
  • the depending claims define further de- velopments of the invention.
  • the inventive component of a turbine comprises a vane, a car ⁇ rier element and at least four interfaces between the vane and the carrier element.
  • the at least four interfaces are sealed by means of leaf seals.
  • the component may comprise at least four leaf seals for connecting the vane and the carrier element at the at least four interfaces. Sealing all four interfaces has the advantage, that a leakage between the vane and the carrier element, for example a carrier ring, can effectively be reduced.
  • the inventive design allows for relative movement between the vane and the carrier element, whilst maintaining a known sealing performance.
  • the leaf seals are a sheetmetal leaf seals.
  • the turbine may comprise a carrier ring which comprises the carrier element.
  • the carrier element can be designed as carrier ring.
  • the leaf seals can be connected to the vane and/or to the carrier element.
  • the leaf seals may be connected to the vane and/or to the carrier element such that a movement between the vane and the carrier element is possi- ble.
  • the turbine may comprise a rotation axis.
  • At least one leaf seal can be connected to the vane and/or to the carrier element such that a movement between the vane and the carrier element in axial direction and/or tangential di ⁇ rection and/or radial direction relative to the rotation axis is possible.
  • at least one leaf seal can be con ⁇ nected to the vane and/or to the carrier element by means of at least one location pin.
  • At least one leaf seal can allow for free movement by using location pins, for example with axial and tangential clearance.
  • At least one leaf seal may comprise means for leading a fluid through the seal.
  • at least one leaf seal may comprise at least one opening, preferably a number of open ⁇ ings, for leading a fluid through the seal.
  • the vane may com- prise a platform with an underside where the vane is con ⁇ nected to the carrier element and which may possibly be ex ⁇ posed to hot gases.
  • the leakage across one of the seals can be allowed to be a higher value compared with one of the other seals in order to supply cooling air to the underside of the platform of the vane. This allows for cool ⁇ ing the underside of the platform.
  • the turbine can comprise a rotation axis and the vane can comprise a trailing edge, a leading edge, a radially outer platform with a leading edge side and a trailing edge side, and a radially inner platform with a leading edge side and a trailing edge side.
  • a first interface can be located at the leading edge side of the radially outer platform.
  • a second interface can be located at the leading edge side of the ra ⁇ dially inner platform.
  • a third interface can be located at the trailing edge side of the radially outer platform.
  • a fourth interface can be located at the trailing edge side of the radially inner platform.
  • the turbine can be a gas turbine or a steam tur ⁇ bine .
  • the inventive method for sealing against leakage between a vane and a carrier element of a turbine component regards to a turbine component which comprises at least four interfaces between the vane and the carrier element.
  • the at least four interfaces are sealed by means of leaf seals.
  • the inventive method can be performed by means of the inventive component as previously described. Therefore, the inventive method has the same advantages as the inventive component.
  • the at least four interfaces may comprise the for ⁇ merly described first interface and/or second interface and/or third interface and/or fourth interface.
  • a fluid is led through the leaf seal, for ex- ample through openings of the leaf seal.
  • air especially cooling air, may be led through the leaf seal. This provides for an effective cooling of the sealed por ⁇ tions, especially of the underside of the platform of the vane .
  • the leaf seal may for instants be an apex seal, a seal face, a sealing strip, a lip seal, a gasket, a sealing washer or a seal washer .
  • the term "carrier element" is de ⁇ fined as an element to which the vane is connected.
  • the car ⁇ rier element may hold the vane in its correct position, for example in a turbine.
  • a vane may typically be connected to at least two carrier elements.
  • the vane may comprise a radially inner platform, an airfoil portion and a radially outer platform.
  • the airfoil portion is located between the two plat ⁇ forms.
  • each platform is connected to a carrier element .
  • Fig. 1 schematically shows a gas turbine.
  • Fig. 2 schematically shows an inventive component of a
  • Fig. 3 schematically shows a leaf seal connected to the platform of a vane in a perspective view.
  • FIG. 1 schematically shows a gas turbine.
  • a gas turbine comprises a rotation axis with a rotor.
  • the rotor comprises a shaft 107.
  • a suction portion with a casing 109, a compressor 101, a combustion portion 151, a turbine 105 and an exhaust portion with a casing 190 are located.
  • the combustion portion 151 communicates with a hot gas flow channel which may have a circular cross section, for example.
  • the turbine 105 comprises a number of turbine stages. Each turbine stage comprises rings of turbine blades. In flow di ⁇ rection of the hot gas in the hot gas flow channel a ring of turbine guide vanes 117 is followed by a ring of turbine ro ⁇ tor blades 115.
  • the turbine guide vanes 117 are connected to an inner casing of a stator.
  • the turbine rotor blades 115 are connected to the rotor.
  • the rotor is connected to a genera- tor, for example.
  • FIG. 2 schematically shows part of a turbine in a sectional view.
  • the axial direction is designated by reference numeral 50
  • the radial direction is designated by reference numeral 51
  • the tangential direction is designated by reference numeral 52.
  • a vane 117 is connected to a number of carrier elements 6, 7, 8, 9.
  • the vane 117 comprises a leading edge 4 and a trailing edge 5.
  • the flow direction of the driving medium, for example gas or steam is indicated by an arrow 1.
  • the vane 117 comprises a radially outer platform 2 and a ra ⁇ dially inner platform 3.
  • the radially outer platform 2 comprises a leading edge side 45 corresponding to the leading edge 4 of the vane 117 and a trailing edge side 47 corre- sponding to the trailing edge 5 of the vane 117.
  • the radially inner platform 3 comprises a leading edge side 46 correspond ⁇ ing to the leading edge 4 of the vane 117 and a trailing edge side 48 corresponding to the trailing edge 5 of the vane 117.
  • the radially outer platform 2 comprises a first protrusion 41 which is located at the leading edge side 45 of the radially outer platform 2 and a second protrusion 43 which is located at the trailing edge side 47 of the radially outer platform 2.
  • the radially inner platform 3 comprises a first protrusion 42 at the leading edge side 46 and a second protrusion 44 at the trailing edge side 48.
  • a first interface is formed between a radially outer surface 31 of the first protrusion 41 of the radially outer platform
  • a second interface is formed between a radially inner surface 32 of the first protrusion 42 of the radially inner platform
  • a third interface is formed by a radially outer surface 33 of the second protrusion 43 of the radially outer platform 2 and a corresponding surface 23 of the carrier element 6. This third interface is sealed by means of a third leaf seal 13.
  • a fourth interface is formed between a radially inner surface 34 of the second protrusion 44 of the radially inner platform 3 and a corresponding surface 24 of the carrier element 8. This fourth interface is sealed by means of a fourth leaf seal 14.
  • the first leaf seal 11 can be connected to the carrier ele ⁇ ment 7 and/or to the radially outer platform 2, preferably to the first protrusion 41 of the radially outer platform 2, by means of retaining pins 15.
  • the second leaf seal 12 can be connected to the carrier element 9 and/or to the radially in ⁇ ner platform 3, preferably to the first protrusion 42 of the radially inner platform 3, by means of retaining pins 15.
  • the third leaf seal 13 can be connected to the carrier element 6 and/or to the radially outer platform 2, preferably to the second protrusion 43 of the radially outer platform 2, by means of retaining pins 15.
  • the fourth leaf seal 14 can be connected to the carrier element 8 and/or to the radially in ⁇ ner platform 3, for example to the second protrusion 44 of the radially inner platform 3, by means of retaining pins 15.
  • All leaf seals 11, 12, 13, 14 can advantageously be sheet- metal leaf seals.
  • the retaining pins or location pins 15 which are used for connecting the leaf seals 11, 12, 13, 14 to the platforms 2, 3 and/or to the carrier elements 6, 7, 8, 9, are constructed such that a free movement between the platforms 2, 3 and the carrier elements 6, 7, 8, 9 is possible.
  • location pins with axial and tangential clearance are used. Retaining pins or location pins 15 allow for relative movement between the vane 117 and the corre ⁇ sponding carrier elements 6, 7, 8, 9, whilst the sealing performance is maintained.
  • the carrier elements 6, 7, 8, 9 can be part of carrier rings.
  • the carrier element 6 and/or the carrier element 7 can be part of a radially outer carrier ring.
  • the carrier element 8 and/or the carrier element 9 can be part of a radially inner carrier ring.
  • a space 10 is formed under the radially outer platform 2.
  • a space 20 is formed under the radially inner platform 3.
  • FIG. 3 schematically shows a leaf seal connected to a plat ⁇ form of a vane in a perspective view.
  • the trail ⁇ ing edge side 48 of the radially inner platform 3 is shown as an example.
  • the leaf seal 14 is connected to the second pro- trusion 14 of the radially inner platform 3 by means of re ⁇ taining pins or location pins 15.
  • openings 17 are shown, which are located in an impingement plate at the underside of the plat- form 3. These openings 17 can be used for cooling the under ⁇ side of the platform 3 and/or for cooling vane 117.
  • the leaf seal 14 further comprises a number of openings 16. These openings 16 preferably have a smaller diameter than the openings 17 in the impingement plate at the underside of the platform 3.
  • the openings 16 of the leaf seal 14 can be used for supplying cooling air or any other cooling medium to the underside of the platform 3.
  • the leakage across one of the seals 11, 12, 13, 14 can be allowed to be of a higher value in order to supply cooling air to the underside of the platform 3.
  • the arrangement shown in Figure 3 has the advantage that a sealing against leakage of hot combustion gasses is provided, whilst at the same time a cooling of the underside of the platform 3 can be performed.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gasket Seals (AREA)

Abstract

A component of a turbine (105) comprising a vane (117), a carrier element (6, 7, 8, 9) and at least four interfaces between the vane (117) and the carrier element (6, 7, 8, 9) is disclosed. The at least four interfaces are sealed by means of leaf seals (11, 12, 13, 14). Moreover, a method for sealing against leakage between a vane (117) and a carrier element (6, 7, 8, 9) of a turbine component is described. The turbine component comprises at least four interfaces between the vane (117) and the carrier element (6, 7, 8, 9). The at least four interfaces are sealed by means of leaf seals (11, 12, 13, 14).

Description

Description
Component of a turbine with leaf seals and method for sealing against leakage between a vane and a carrier element
The present invention relates to a component of a turbine. It further relates to a method for sealing against leakage be¬ tween a vane and a carrier element of a turbine component. The air leakage between a turbine vane axial face and the corresponding feature of the carrier ring is required to be limited to a minimum. The turbine vane and carrier rings are subjected to thermal and mechanical loads which induce dis¬ tortion and relative movement. Therefore, leakage between a turbine vane and the corresponding feature of the carrier ring may occur.
Previously, air leakage has been minimised with direct face- to-face contact, but has been prone to an unknown rate of leakage during service.
In US 4,815,933 a boltless turbine nozzle and a nozzle sup¬ port assembly that includes a turbine nozzle mounting flange seated in a nozzle seat forming a part of the nozzle support are disclosed. A pressure actuated pliable seal is affixed to the turbine nozzle adjacent to the nozzle seat in order to provide an air seal across the completed assembly.
In EP 1 340 885 A2 a leaf seal support for a gas turbine en- gine nozzle vane is described. The turbine nozzle assembly includes a plurality of segments joint together to form an outer band and a plurality of segments joined together to form an inner band. At least to one airfoil is positioned be¬ tween the outer and inner bands. A leaf seal is attached to each inner band segment by at least one pin member and a leaf seal is attached to each outer band segment by at least one pin member. In US 5,118,120 an apparatus for effecting a seal between two structural components of a turbo machine or similar device is disclosed. The apparatus comprises a leaf seal located in the space between the two components.
In US 5,797,723 and EP 0 526 058 Al a turbine seal is dis¬ closed. The turbine seal includes a first arcuate segment de¬ fining a flowpath boundary between combustion gases and air and includes a radially outwardly extending rail at one end thereof. A second arcuate segment is disposed coaxially with the first segment for defining a continuation of the flowpath boundary. It has a radially extending face adjoining the rail. A leaf seal bridges the rail and the face for sealing leakage there between. A plurality of pins extended through the leaf seal for providing the mounting to the rail.
In EP 1 445 537 A2 an assembly for providing a seal at an aft end of a combustor liner for a gas turbine engine is de¬ scribed. The sealing assembly includes a substantially annu- lar first sealing member positioned between an aft portion of a support member and the liner aft end so as to seat on a designated surface portion of the liner aft end. A substan¬ tially annular second sealing member is positioned between the support member aft portion and a turbine nozzle located downstream of the liner aft end so as to seat on a designated surface portion of the support member aft portion. The first and second sealing members are maintained in their respective seating positions as the support member aft portion moves ra¬ dially or axially with respect to the liner aft end and ra- dially or axially with respect to the turbine nozzle. The first and second sealing members allow for axially and ra¬ dially movement of the adjacent components.
In DE 103 06 915 Al a sealing arrangement for gas turbines is disclosed. The described sealing member comprises a number of openings through which a fluid can pass the sealing member. In WO 2005/033558 Al a seal which comprises a first and a second component is disclosed. The seal is applied to a com¬ bustion chamber for a gas turbine. It comprises a spring load which provides a seal also in the case of vibrations in the combustion chamber. The seal is further applied to the seal¬ ing between adjacent stationary blade platforms in gas turbines. The seal comprises a number of openings for leading a fluid through the seal . US 5,343,694 a gas turbine nozzle including a plurality of nozzle segments having a pair of nozzle vanes supported by inner and outer shroud segments is disclosed. The outer shroud segment includes a generally axially extending plat¬ form with a circumferentially extending seal member attached to the upstream end thereof to seal with the combustor liner flange against the leakage there between. Moreover, a ra¬ dially extending circumferential projection is attached to the downstream end of the platform for providing an engagement surface for a W seal to prevent leakage between the outer rotor casing and the shroud segment.
In WO 2009/085949 Al and US 2009/0169370 Al a turbine nozzle segment including a band having a plurality of tabs is dis¬ closed. An airfoil extending from the band and a support structure attached to the tabs is described. The support structure has a plurality of biasing structures.
In US 2009/0074562 Al a turbine nozzle guide vane with pas¬ sages leading from a hollow core to respective seal strip slots to deliver cooling air to abutment faces on each end of the vane is disclosed.
In EP 2 180 143 Al a gas turbine nozzle arrangement is dis¬ closed. It comprises at least one seal strip which is present between a radially outer surface of a carrier ring section and inner surface of an inner platform and comprises openings for allowing cooling fluid to flow through the seal strip. The document EP 1 296 023 Al discloses a devise for holding strip sealing gaskets on a turbo machine nozzle.
The document WO 2009/158554 A2 describes a seal for contain- ment of fluids or gases during high temperature applications.
In US 5,118,120 entitled "leaf seal" an apparatus for effect¬ ing a seal between two structure components of a turbo ma¬ chine is taught, comprising a leaf seal located in the space between the two components and a spring which continuously biases the leaf seal into a sealing position against the com¬ ponents regardless of the pressure differential across the leaf seal . It is a first objective of the present invention to provide a component of a turbine with a reduced leakage between a vane and a carrier element. It is a second objective of the pre¬ sent invention to provide a method for sealing against leak¬ age between a vane and a carrier element of a turbine compo- nent .
The first objective is solved by a component as claimed in claim 1. The second objective is solved by a method as claimed in claim 12. The depending claims define further de- velopments of the invention.
The inventive component of a turbine comprises a vane, a car¬ rier element and at least four interfaces between the vane and the carrier element. The at least four interfaces are sealed by means of leaf seals. For example, the component may comprise at least four leaf seals for connecting the vane and the carrier element at the at least four interfaces. Sealing all four interfaces has the advantage, that a leakage between the vane and the carrier element, for example a carrier ring, can effectively be reduced. At the same time the inventive design allows for relative movement between the vane and the carrier element, whilst maintaining a known sealing performance. Preferably, the leaf seals are a sheetmetal leaf seals. The turbine may comprise a carrier ring which comprises the carrier element. Alternatively, the carrier element can be designed as carrier ring.
Generally, the leaf seals can be connected to the vane and/or to the carrier element. Advantageously, the leaf seals may be connected to the vane and/or to the carrier element such that a movement between the vane and the carrier element is possi- ble. For example, the turbine may comprise a rotation axis.
At least one leaf seal can be connected to the vane and/or to the carrier element such that a movement between the vane and the carrier element in axial direction and/or tangential di¬ rection and/or radial direction relative to the rotation axis is possible. Preferably, at least one leaf seal can be con¬ nected to the vane and/or to the carrier element by means of at least one location pin. At least one leaf seal can allow for free movement by using location pins, for example with axial and tangential clearance.
At least one leaf seal may comprise means for leading a fluid through the seal. For example, at least one leaf seal may comprise at least one opening, preferably a number of open¬ ings, for leading a fluid through the seal. The vane may com- prise a platform with an underside where the vane is con¬ nected to the carrier element and which may possibly be ex¬ posed to hot gases. For example, the leakage across one of the seals can be allowed to be a higher value compared with one of the other seals in order to supply cooling air to the underside of the platform of the vane. This allows for cool¬ ing the underside of the platform.
The turbine can comprise a rotation axis and the vane can comprise a trailing edge, a leading edge, a radially outer platform with a leading edge side and a trailing edge side, and a radially inner platform with a leading edge side and a trailing edge side. A first interface can be located at the leading edge side of the radially outer platform. A second interface can be located at the leading edge side of the ra¬ dially inner platform. A third interface can be located at the trailing edge side of the radially outer platform. A fourth interface can be located at the trailing edge side of the radially inner platform. These four interfaces can each be sealed by means of a previously described leaf seal.
Generally, the turbine can be a gas turbine or a steam tur¬ bine .
The inventive method for sealing against leakage between a vane and a carrier element of a turbine component regards to a turbine component which comprises at least four interfaces between the vane and the carrier element. The at least four interfaces are sealed by means of leaf seals. The inventive method can be performed by means of the inventive component as previously described. Therefore, the inventive method has the same advantages as the inventive component. Generally, the at least four interfaces may comprise the for¬ merly described first interface and/or second interface and/or third interface and/or fourth interface.
Advantageously a fluid is led through the leaf seal, for ex- ample through openings of the leaf seal. Advantageously, air, especially cooling air, may be led through the leaf seal. This provides for an effective cooling of the sealed por¬ tions, especially of the underside of the platform of the vane .
In the context of the present invention the term "leaf seal" is used with the same meaning as the term is used in the cited state of the art documents, for example in US
5,118,120, WO 2009/085949 Al or US 2009/0169370 Al . The leaf seal may for instants be an apex seal, a seal face, a sealing strip, a lip seal, a gasket, a sealing washer or a seal washer . In the present invention, the term "carrier element" is de¬ fined as an element to which the vane is connected. The car¬ rier element may hold the vane in its correct position, for example in a turbine. A vane may typically be connected to at least two carrier elements. The vane may comprise a radially inner platform, an airfoil portion and a radially outer platform. The airfoil portion is located between the two plat¬ forms. Preferably, each platform is connected to a carrier element .
Further features, properties and advantages of the present invention will become clear from the following description of an embodiment in conjunction with the accompanying drawings. All mentioned features are advantageous alone or in any com¬ bination with each other.
Fig. 1 schematically shows a gas turbine.
Fig. 2 schematically shows an inventive component of a
turbine in a sectional view.
Fig. 3 schematically shows a leaf seal connected to the platform of a vane in a perspective view.
An embodiment of the present invention will now be described with reference to Figures 1 to 3.
Figure 1 schematically shows a gas turbine. A gas turbine comprises a rotation axis with a rotor. The rotor comprises a shaft 107. Along the rotor a suction portion with a casing 109, a compressor 101, a combustion portion 151, a turbine 105 and an exhaust portion with a casing 190 are located.
The combustion portion 151 communicates with a hot gas flow channel which may have a circular cross section, for example. The turbine 105 comprises a number of turbine stages. Each turbine stage comprises rings of turbine blades. In flow di¬ rection of the hot gas in the hot gas flow channel a ring of turbine guide vanes 117 is followed by a ring of turbine ro¬ tor blades 115. The turbine guide vanes 117 are connected to an inner casing of a stator. The turbine rotor blades 115 are connected to the rotor. The rotor is connected to a genera- tor, for example.
During operation of the gas turbine air is sucked and com¬ pressed by means of the compressor 101. The compressed air is led to the combustion portion 151 and is mixed with fuel. The mixture of air and fuel is then combusted. The resulting hot combustion gas flows through a hot gas flow channel to the turbine guide vanes 117 and the turbine rotor blades 115 and actuates the rotor. The rotation axis of the turbine is des¬ ignated by reference numeral 102.
Figure 2 schematically shows part of a turbine in a sectional view. The axial direction is designated by reference numeral 50, the radial direction is designated by reference numeral 51 and the tangential direction is designated by reference numeral 52. In Figure 2 a vane 117 is connected to a number of carrier elements 6, 7, 8, 9. The vane 117 comprises a leading edge 4 and a trailing edge 5. The flow direction of the driving medium, for example gas or steam is indicated by an arrow 1.
The vane 117 comprises a radially outer platform 2 and a ra¬ dially inner platform 3. The radially outer platform 2 comprises a leading edge side 45 corresponding to the leading edge 4 of the vane 117 and a trailing edge side 47 corre- sponding to the trailing edge 5 of the vane 117. The radially inner platform 3 comprises a leading edge side 46 correspond¬ ing to the leading edge 4 of the vane 117 and a trailing edge side 48 corresponding to the trailing edge 5 of the vane 117. By connecting the vane 117 to a number of carrier elements 6, 7, 8, 9 a number of interfaces between the vane 117 and the carrier element 6, 7, 8, 9 are established. The radially outer platform 2 comprises a first protrusion 41 which is located at the leading edge side 45 of the radially outer platform 2 and a second protrusion 43 which is located at the trailing edge side 47 of the radially outer platform 2. The radially inner platform 3 comprises a first protrusion 42 at the leading edge side 46 and a second protrusion 44 at the trailing edge side 48.
A first interface is formed between a radially outer surface 31 of the first protrusion 41 of the radially outer platform
2 and a corresponding surface 21 of the carrier element 7. This first interface is sealed by means of a first leaf seal 11.
A second interface is formed between a radially inner surface 32 of the first protrusion 42 of the radially inner platform
3 and a corresponding surface 22 of the carrier element 9. This second interface is sealed by means of a second leaf seal 12.
A third interface is formed by a radially outer surface 33 of the second protrusion 43 of the radially outer platform 2 and a corresponding surface 23 of the carrier element 6. This third interface is sealed by means of a third leaf seal 13.
A fourth interface is formed between a radially inner surface 34 of the second protrusion 44 of the radially inner platform 3 and a corresponding surface 24 of the carrier element 8. This fourth interface is sealed by means of a fourth leaf seal 14.
The first leaf seal 11 can be connected to the carrier ele¬ ment 7 and/or to the radially outer platform 2, preferably to the first protrusion 41 of the radially outer platform 2, by means of retaining pins 15. The second leaf seal 12 can be connected to the carrier element 9 and/or to the radially in¬ ner platform 3, preferably to the first protrusion 42 of the radially inner platform 3, by means of retaining pins 15. The third leaf seal 13 can be connected to the carrier element 6 and/or to the radially outer platform 2, preferably to the second protrusion 43 of the radially outer platform 2, by means of retaining pins 15. The fourth leaf seal 14 can be connected to the carrier element 8 and/or to the radially in¬ ner platform 3, for example to the second protrusion 44 of the radially inner platform 3, by means of retaining pins 15.
All leaf seals 11, 12, 13, 14 can advantageously be sheet- metal leaf seals. Preferably, the retaining pins or location pins 15 which are used for connecting the leaf seals 11, 12, 13, 14 to the platforms 2, 3 and/or to the carrier elements 6, 7, 8, 9, are constructed such that a free movement between the platforms 2, 3 and the carrier elements 6, 7, 8, 9 is possible. Preferably, location pins with axial and tangential clearance are used. Retaining pins or location pins 15 allow for relative movement between the vane 117 and the corre¬ sponding carrier elements 6, 7, 8, 9, whilst the sealing performance is maintained.
Generally, the carrier elements 6, 7, 8, 9 can be part of carrier rings. For example, the carrier element 6 and/or the carrier element 7 can be part of a radially outer carrier ring. The carrier element 8 and/or the carrier element 9 can be part of a radially inner carrier ring.
Radially outside of the radially outer platform 2 a space 10 is formed under the radially outer platform 2. Radially in¬ side of the radially inner platform 3 a space 20 is formed under the radially inner platform 3. The leaf seals 11, 12,
13, 14 effectively prevent a leakage of hot gases from a com¬ bustion chamber of the gas or steam turbine into the spaces 10 and 20 under the platforms 2 and 3. At the same time a movement between the vane 117 and the carrier element 6, 7, 8, 9, for example due to vibrations, is possible, whilst the sealing function of the leaf seals 11, 12, 13, 14 is maintained . Figure 3 schematically shows a leaf seal connected to a plat¬ form of a vane in a perspective view. In Figure 3 the trail¬ ing edge side 48 of the radially inner platform 3 is shown as an example. The leaf seal 14 is connected to the second pro- trusion 14 of the radially inner platform 3 by means of re¬ taining pins or location pins 15.
Additionally, a number of openings 17 are shown, which are located in an impingement plate at the underside of the plat- form 3. These openings 17 can be used for cooling the under¬ side of the platform 3 and/or for cooling vane 117.
The leaf seal 14 further comprises a number of openings 16. These openings 16 preferably have a smaller diameter than the openings 17 in the impingement plate at the underside of the platform 3. The openings 16 of the leaf seal 14 can be used for supplying cooling air or any other cooling medium to the underside of the platform 3. Preferably, the leakage across one of the seals 11, 12, 13, 14 can be allowed to be of a higher value in order to supply cooling air to the underside of the platform 3.
The arrangement shown in Figure 3 has the advantage that a sealing against leakage of hot combustion gasses is provided, whilst at the same time a cooling of the underside of the platform 3 can be performed.
The other three leaf seals 11, 12, 13 can be constructed and connected in the same way as shown in Figure 3.

Claims

Claims
1. A component of a turbine (105) comprising a vane (117), a carrier element (6, 7, 8, 9) and at least four interfaces be- tween the vane (117) and the carrier element (6, 7, 8, 9), characterised in that
the at least four interfaces are sealed by means of leaf seals (11, 12, 13, 14) .
2. The component as claimed in claim 1,
characterised in that
the leaf seals (11, 12, 13, 14) are sheetmetal leaf seals.
3. The component as claimed in claim 1 or 2,
characterised in that
the turbine (105) comprises a carrier ring which comprises the carrier element (6, 7, 8, 9) .
4. The component as claimed in any of the claims 1 to 3, characterised in that
the leaf seals (11, 12, 13, 14) are connected to the vane (117) and/or to the carrier element (6, 7, 8, 9) .
5. The component as claimed in claim 4,
characterised in that
at least one leaf seal (11, 12, 13, 14) is connected to the vane (117) and/or to the carrier element (6, 7, 8, 9) such that a movement between the vane (117) and the carrier ele¬ ment (6, 7, 8, 9) is possible.
6. The component as claimed in claim 5,
characterised in that
the turbine (105) comprises a rotation axis (102) and at least one leaf seal (11, 12, 13, 14) is connected to the vane (117) and/or to the carrier element (6, 7, 8, 9) such that a movement between the vane (117) and the carrier element (6,
7. 8, 9) in axial (50) and/or tangential (52) and/or radial (51) direction is possible.
7. The component as claimed in any of the claims 1 to 6, characterised in that
at least one leaf seal (11, 12, 13, 14) is connected to the vane (117) and/or to the carrier element (6, 7, 8, 9) by means of at least one location pin (15) .
8. The component as claimed in any of the claims 1 to 7, characterised in that
at least one leaf seal comprises means for leading a fluid through the seal .
9. The component as claimed in any of the claims 1 to 8, characterised in that
at least one leaf seal (11, 12, 13, 14) comprises at least one opening (16) for leading a fluid through the seal (11, 12, 13, 14) .
10. The component as claimed in any of the claims 1 to 9, characterised in that
the turbine (105) comprises a rotation axis (102) and the vane (117) comprises a trailing edge (5), a leading edge (4), a radially outer platform (2) with a leading edge side (45) and a trailing edge side (47), and a radially inner platform (3) with a leading edge side (46) and a trailing edge side (48), and a first interface is located at the leading edge side (45) of the radially outer platform (2), a second inter¬ face is located at the leading edge side (46) of the radially inner platform (3) , a third interface is located at the trailing edge side (47) of the radially outer platform (2) and a fourth interface is located at the trailing edge side (48) of the radially inner platform (3) .
11. The component as claimed in any of the claims 1 to 10, characterised in that
the turbine (105) is a gas turbine or a steam turbine.
12. A method for sealing against leakage between a vane (117) and a carrier element (6, 7, 8, 9) of a turbine component, wherein the turbine component comprises at least four inter¬ faces between the vane (117) and the carrier element (6, 7, 8, 9),
characterised in
sealing the at least four interfaces by means of leaf seals (11, 12, 13, 14) . 13. The method as claimed in claim 12,
characterised in
leading a fluid through the leaf seal (11, 12,
13, 14) .
14. The method as claimed in claim 13,
characterised in
leading a fluid through openings of the leaf seal (11, 12,
13, 14) .
15. The method as claimed in claim 13 or 14,
characterised in
leading air through the leaf seal (11, 12, 13, 14) .
PCT/EP2011/061641 2010-08-05 2011-07-08 Component of a turbine with leaf seals and method for sealing against leakage between a vane and a carrier element WO2012016790A1 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
RU2013109413/06A RU2583487C2 (en) 2010-08-05 2011-07-08 Turbine component with plate seals and method of sealing against leak between blade and carrying element
CN201180038491.3A CN103052766B (en) 2010-08-05 2011-07-08 Have the turbo machine of sheet Sealing parts and for carrying out the method sealing to prevent from leaking between guide plate and load-carrying unit
US13/812,153 US9506374B2 (en) 2010-08-05 2011-07-08 Component of a turbine with leaf seals and method for sealing against leakage between a vane and a carrier element
EP11732428.5A EP2564032B1 (en) 2010-08-05 2011-07-08 Component of a turbine with leaf seals and method for sealing against leakage between a vane and a carrier element

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP10171961A EP2415969A1 (en) 2010-08-05 2010-08-05 Component of a turbine with leaf seals and method for sealing against leakage between a vane and a carrier element
EP10171961.5 2010-08-05

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US (1) US9506374B2 (en)
EP (2) EP2415969A1 (en)
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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10822977B2 (en) 2016-11-30 2020-11-03 General Electric Company Guide vane assembly for a rotary machine and methods of assembling the same

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9851008B2 (en) * 2012-06-04 2017-12-26 United Technologies Corporation Seal land for static structure of a gas turbine engine
US9140133B2 (en) 2012-08-14 2015-09-22 United Technologies Corporation Threaded full ring inner air-seal
US9102098B2 (en) 2012-12-05 2015-08-11 Wobbleworks, Inc. Hand-held three-dimensional drawing device
EP2801702B1 (en) * 2013-05-10 2020-05-06 Safran Aero Boosters SA Inner shroud of turbomachine with abradable seal
US9988932B2 (en) 2013-12-06 2018-06-05 Honeywell International Inc. Bi-cast turbine nozzles and methods for cooling slip joints therein
US9885245B2 (en) 2014-05-20 2018-02-06 Honeywell International Inc. Turbine nozzles and cooling systems for cooling slip joints therein
EP3029378B1 (en) * 2014-12-04 2019-08-28 Ansaldo Energia Switzerland AG Sequential burner for an axial gas turbine
US10385712B2 (en) * 2015-05-22 2019-08-20 United Technologies Corporation Support assembly for a gas turbine engine
US10113436B2 (en) 2016-02-08 2018-10-30 United Technologies Corporation Chordal seal with sudden expansion/contraction
US10494936B2 (en) * 2016-05-23 2019-12-03 United Technologies Corporation Fastener retention mechanism
US10822987B1 (en) * 2019-04-16 2020-11-03 Pratt & Whitney Canada Corp. Turbine stator outer shroud cooling fins
US11174742B2 (en) 2019-07-19 2021-11-16 Rolls-Royce Plc Turbine section of a gas turbine engine with ceramic matrix composite vanes
US11761342B2 (en) * 2020-10-26 2023-09-19 General Electric Company Sealing assembly for a gas turbine engine having a leaf seal

Citations (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4815933A (en) 1987-11-13 1989-03-28 The United States Of America As Represented By The Secretary Of The Air Force Nozzle flange attachment and sealing arrangement
US5118120A (en) 1989-07-10 1992-06-02 General Electric Company Leaf seals
EP0526058A1 (en) 1991-07-22 1993-02-03 General Electric Company Turbine Nozzle Support
EP0716220A1 (en) * 1994-12-07 1996-06-12 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Undivided stator ring for a turbomachine
US5797723A (en) 1996-11-13 1998-08-25 General Electric Company Turbine flowpath seal
EP1296023A1 (en) 2001-09-20 2003-03-26 Snecma Moteurs Fixing device for seal strips
EP1340885A2 (en) 2002-02-27 2003-09-03 General Electric Company Leaf seal support for a gas turbine engine nozzle vane
US6666645B1 (en) * 2000-01-13 2003-12-23 Snecma Moteurs Arrangement for adjusting the diameter of a gas turbine stator
EP1445537A2 (en) 2003-02-10 2004-08-11 General Electric Company Sealing assembly for the aft end of a ceramic matrix composite liner in a gas turbine engine combustor
DE10306915A1 (en) 2003-02-19 2004-09-02 Alstom Technology Ltd Seal for use between segments of gas turbine shrouds comprises strip with apertures for passage of gas in pattern designed so that when strip shifts sideways their free cross-section remains constant
WO2005033558A1 (en) 2003-10-02 2005-04-14 Alstom Technology Ltd High temperature seal
US20090074562A1 (en) 2003-12-12 2009-03-19 Self Kevin P Nozzle guide vanes
US20090169370A1 (en) 2007-12-29 2009-07-02 General Electric Company Turbine nozzle segment
WO2009158554A2 (en) 2008-06-27 2009-12-30 Halling Horace P Gas turbine nozzle seals for 2000o f gas containment
EP2180143A1 (en) 2008-10-23 2010-04-28 Siemens Aktiengesellschaft Gas turbine nozzle arrangement and gas turbine

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU1200609A1 (en) * 1984-03-01 1990-10-30 Предприятие П/Я А-1469 Nozzle unit of gas turbine
US4712979A (en) * 1985-11-13 1987-12-15 The United States Of America As Represented By The Secretary Of The Air Force Self-retained platform cooling plate for turbine vane
FR2786222B1 (en) * 1998-11-19 2000-12-29 Snecma LAMELLE SEALING DEVICE
US6347508B1 (en) * 2000-03-22 2002-02-19 Allison Advanced Development Company Combustor liner support and seal assembly

Patent Citations (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4815933A (en) 1987-11-13 1989-03-28 The United States Of America As Represented By The Secretary Of The Air Force Nozzle flange attachment and sealing arrangement
US5118120A (en) 1989-07-10 1992-06-02 General Electric Company Leaf seals
EP0526058A1 (en) 1991-07-22 1993-02-03 General Electric Company Turbine Nozzle Support
US5343694A (en) 1991-07-22 1994-09-06 General Electric Company Turbine nozzle support
EP0716220A1 (en) * 1994-12-07 1996-06-12 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Undivided stator ring for a turbomachine
US5797723A (en) 1996-11-13 1998-08-25 General Electric Company Turbine flowpath seal
US6666645B1 (en) * 2000-01-13 2003-12-23 Snecma Moteurs Arrangement for adjusting the diameter of a gas turbine stator
EP1296023A1 (en) 2001-09-20 2003-03-26 Snecma Moteurs Fixing device for seal strips
EP1340885A2 (en) 2002-02-27 2003-09-03 General Electric Company Leaf seal support for a gas turbine engine nozzle vane
EP1445537A2 (en) 2003-02-10 2004-08-11 General Electric Company Sealing assembly for the aft end of a ceramic matrix composite liner in a gas turbine engine combustor
DE10306915A1 (en) 2003-02-19 2004-09-02 Alstom Technology Ltd Seal for use between segments of gas turbine shrouds comprises strip with apertures for passage of gas in pattern designed so that when strip shifts sideways their free cross-section remains constant
WO2005033558A1 (en) 2003-10-02 2005-04-14 Alstom Technology Ltd High temperature seal
US20090074562A1 (en) 2003-12-12 2009-03-19 Self Kevin P Nozzle guide vanes
US20090169370A1 (en) 2007-12-29 2009-07-02 General Electric Company Turbine nozzle segment
WO2009085949A1 (en) 2007-12-29 2009-07-09 General Electric Company Turbine nozzle segment
WO2009158554A2 (en) 2008-06-27 2009-12-30 Halling Horace P Gas turbine nozzle seals for 2000o f gas containment
EP2180143A1 (en) 2008-10-23 2010-04-28 Siemens Aktiengesellschaft Gas turbine nozzle arrangement and gas turbine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10822977B2 (en) 2016-11-30 2020-11-03 General Electric Company Guide vane assembly for a rotary machine and methods of assembling the same

Also Published As

Publication number Publication date
RU2013109413A (en) 2014-09-10
US20130183150A1 (en) 2013-07-18
EP2564032B1 (en) 2016-05-18
CN103052766A (en) 2013-04-17
US9506374B2 (en) 2016-11-29
EP2564032A1 (en) 2013-03-06
RU2583487C2 (en) 2016-05-10
EP2415969A1 (en) 2012-02-08
CN103052766B (en) 2016-04-27

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